US9222412B2 - Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine - Google Patents

Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine Download PDF

Info

Publication number
US9222412B2
US9222412B2 US13/737,260 US201313737260A US9222412B2 US 9222412 B2 US9222412 B2 US 9222412B2 US 201313737260 A US201313737260 A US 201313737260A US 9222412 B2 US9222412 B2 US 9222412B2
Authority
US
United States
Prior art keywords
engine
aircraft
monitoring parameter
tet
health
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US13/737,260
Other languages
English (en)
Other versions
US20130199204A1 (en
Inventor
Emmanuel Camhi
Guido Borchers
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters SAS
Original Assignee
Airbus Helicopters SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Helicopters SAS filed Critical Airbus Helicopters SAS
Assigned to EUROCOPTER reassignment EUROCOPTER ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Borchers, Guido, CAMHI, EMMANUEL
Publication of US20130199204A1 publication Critical patent/US20130199204A1/en
Assigned to AIRBUS HELICOPTERS reassignment AIRBUS HELICOPTERS CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: EUROCOPTER
Application granted granted Critical
Publication of US9222412B2 publication Critical patent/US9222412B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B23/00—Testing or monitoring of control systems or parts thereof
    • G05B23/02—Electric testing or monitoring
    • G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
    • G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
    • G05B23/0221—Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/82—Forecasts
    • F05D2260/821—Parameter estimation or prediction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/332—Maximum loads or fatigue criteria
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/335—Output power or torque
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
    • F05D2270/803—Sampling thereof

Definitions

  • the present invention relates to a method and to a device making it possible to perform a check of the state of health of a turbine engine arranged on an aircraft, said aircraft being provided with at least one turbine engine.
  • Such an aircraft may be a rotary-wing aircraft, also known as a rotorcraft.
  • the aircraft may also be an aircraft not provided with such a rotary wing.
  • a rotorcraft is piloted while monitoring many instruments on the instrument panel. Most of the instruments represent operation of the power plant of the rotorcraft.
  • rotorcraft are fitted with at least one turboshaft engine having a free turbine for driving a rotary wing in rotation. Drive power is then extracted (taken off) from a low pressure stage of each free turbine, which stage is mechanically independent of the assembly comprising the compressor and the high pressure stage of the engine.
  • Each free turbine of the engines operates at a speed of rotation lying in the range 20,000 revolutions per minute (rpm) to 50,000 rpm, so a speed-reduction gearbox is needed in the connection with the main rotor of the rotorcraft since its speed of rotation lies substantially in the range 200 rpm to 400 rpm: this is referred to as the “main power transmission gearbox” or “MGB”.
  • Thermal limits on the engine and torque limits on the MGB serve to define, for example, three normal utilization ratings for the engine:
  • the engine manufacturer draws up available power curves for an engine as a function of altitude and of temperature, with this being done for each of the above-defined ratings. Similarly, the engine manufacturer determines the life of the engine and the guaranteed minimum power for each rating; this guaranteed minimum power corresponding to the power that the engine will deliver when it has reached the end of its life, such an engine being referred to by convenience as an “aging engine” in the remainder of the text below.
  • the health check may serve to guarantee contingency power in the event of failure of an engine.
  • Such a health check consists in determining the power margin of an engine relative to a minimum power as measured, for example, on a test bench. If the power margin is positive, the engine remains capable of delivering the required power. Otherwise, maintenance action should be undertaken to re-establish the performance of the engine.
  • the health check may be performed by determining a power margin as such, or by determining a margin of a monitoring parameter of the engine relative to a measurement taken on a test bench.
  • an operating margin is determined that can be a power margin or a monitoring parameter margin.
  • two monitoring parameters are used to check the performance of an engine.
  • one monitoring parameter may be the temperature of the gas flowing through said assembly.
  • a first monitoring parameter may be the temperature of the gas at the inlet to the high-pressure turbine, known as the Turbine Entry Temperature or “TET” by the person skilled in the art.
  • the blades of the high pressure turbine of the engine are subjected to centrifugal force and to the temperature TET. Beyond a certain level, the component material of the turbine blades is subjected to creep, resulting in expansion that lengthens the turbine blades. Thus, the turbine blades might touch the casing of the high-pressure turbine and thus be degraded.
  • the temperature TET is thus associated directly with degradation of the engine.
  • the first monitoring parameter may be the temperature of the gas at the entry to the free turbine, known to the person skilled in the art as “T 45 ”. Since this temperature T 45 is a good indicator of the temperature TET, it is representative of the degradation of the engine.
  • a first monitoring parameter is thus the temperature of an assembly having at least one turbine, this temperature possibly being the temperature TET of the gas at the inlet to the high-pressure turbine or the temperature T 45 of the gas at the inlet to the free turbine.
  • a health check may consist in determining a temperature margin relative to a minimum reference temperature.
  • a second monitoring parameter relates to the power delivered by the engine or to the torque from its shaft, where power and shaft torque are mutually dependent.
  • the speed of rotation of the gas generator of the engine known as “Ng” by the person skilled in the art, is also linked with the power delivered by the engine, so the second monitoring parameter that can be used is this speed of rotation of the gas generator.
  • checking the state of health of the engine consists, for example, in:
  • a drive torque and a speed of rotation so as to deduce therefrom the power developed by an engine.
  • the torque exerted on an outlet shaft driven by the free turbine and the speed of rotation of said outlet shaft are measured.
  • the flight is flown with a given speed of rotation Nr of the main rotor, and said torque is measured.
  • a torque margin is deduced.
  • the health check should be performed rigorously because if it is negative, i.e. if the above-mentioned verifications do not give satisfactory results, it has a non-negligible impact on any downtime of the aircraft and on the costs of maintaining said aircraft.
  • the in-flight measurement conditions and for the test-bench measurement conditions are as close as possible.
  • the measurements taken on a test bench are taken under thermally stable conditions.
  • the pilot places the aircraft in a particular stage of flight such as level flight at altitude and speed that are stabilized for several minutes. The pilot can then launch a manual action requesting collection of the monitoring parameters necessary for the health check, and then calculation of at least one operating margin.
  • That method then includes: a step of stabilizing the aircraft, a step of acquiring at least one value for a monitoring parameter, and a step of evaluating an operating margin.
  • a step of maintaining the engine may then be undertaken depending on the results of the evaluation step.
  • Document FR 2 899 640 describes a method of performing a health check on at least a first turbine engine of a rotorcraft, that rotorcraft being provided with first and second engines.
  • Document EP 1 970 786 proposes a method of analyzing the operational data of an engine and potential faults reflected in such data.
  • Document EP 2 202 500 discloses a system for assisting maintenance and operation of a gas turbine.
  • An object of the present invention is to propose a method and a device enabling stability criteria to be established for possibly performing a health check automatically rather than on manual request.
  • the invention provides a method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft, said method comprising an acquisition step for acquiring at least one monitoring parameter of the engine and an evaluation step for evaluating the health of said engine.
  • the aircraft may have a rotary wing.
  • This method is remarkable, in particular, in that determination of whether it is possible to perform the acquisition step takes place automatically, and thus without requiring manual intervention from the pilot.
  • Engine power effects are due, for example to installation losses proper including head-losses in the air inlets of the engines, or else to pressure distortions, or indeed to the nozzles.
  • engine power effects include the power extracted (taken off) from the engine by accessories, the altitude of the aircraft, and the outside temperature, in particular.
  • the engine for checking can be relatively stable during such a stage of flight, the operating conditions then being very similar to the operating conditions on a test bench.
  • the stability of at least one monitoring parameter is then verified by:
  • the engine is sufficiently stable to perform a health check that is effective and accurate.
  • the two established criteria thus enable a health check to be triggered automatically in flight, without disturbing flight. Similarly, this method makes it possible to avoid forcing the pilot to stabilize the aircraft in predetermined manner.
  • the acquisition step and then the evaluation step are performed. This evaluation step can then lead to a maintenance step.
  • the method may also have one or more of the following characteristics.
  • the forward speed of the aircraft is measured, and data relating to the altitude of the aircraft is measured, the aircraft being considered to be flying in level forward flight if the forward speed is greater than a minimum speed defined by the manufacturer and if, over a given length of time, variation in the data relating to altitude is less than a constant defined by the manufacturer.
  • Such data relating to the altitude may be either the pressure altitude of the aircraft, or the outside pressure of the air outside the aircraft.
  • the first duration and the second duration optionally end at the same time.
  • the two established stability criteria are then verified at the same time.
  • the first duration is 4 minutes
  • the second duration is 30 seconds in order to optimize the results.
  • each monitoring parameter is chosen from a list including at least one of the following parameters: the speed of rotation Ng of a gas generator of said engine; a temperature TET of the gas at the inlet of a high-pressure turbine of the engine; a temperature T 45 of the gas at the inlet of a free turbine of said engine; a torque delivered by the engine; and an inlet temperature T 1 of the air at the inlet of the engine.
  • the first threshold is: 2% for the speed of rotation Ng of the gas generator of said engine; 15 degrees Celsius (° C.) for the temperature TET of the gas at the inlet of a high-pressure turbine of the engine and for the temperature T 45 of the gas at the inlet of a free turbine of said engine; 2% for torque delivered by the engine; and 2° C. for the inlet temperature T 1 of the air at the inlet of the engine.
  • the second threshold may be: 0.5% for the speed of rotation Ng of the gas generator of said engine; 5° C. for the temperature TET of the gas at the inlet of a high-pressure turbine of the engine and for the temperature T 45 of the gas at the inlet of a free turbine of said engine; 0.5% for torque delivered by the engine; and 0.5° C. for the inlet temperature T 1 of the air at the inlet of the engine.
  • a moving average is taken of the value of each monitoring parameter over a period defined by the manufacturer.
  • the moving average corresponds to the average of the value of each monitoring parameter during the last 20 seconds.
  • said moving average is subtracted from the value of the signal corresponding to said monitoring parameter at said given instant.
  • an acquisition step can be triggered.
  • a warning may be generated for informing the pilot in order to avoid the pilot taking any sudden action.
  • the health check is performed automatically. The pilot is thus informed so that said pilot does not destabilize operation of the engine.
  • the health check may be canceled automatically so as not to generate results that are not representative of the real health of the engine being checked.
  • the method may include control logic for checking the engines one after another.
  • the method is applied to the second engine.
  • the stability of at least one monitoring parameter of the engine may be verified again, and the acquisition step triggered if each monitoring parameter is stable.
  • first and second durations are implemented as during the initial stability verification, or else to implement different and optionally shorter first and second durations.
  • the invention also provides a health-check device for automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft, said check comprising an acquisition step of acquiring at least one monitoring parameter of the engine and an evaluation step of evaluating the health of said engine for checking, wherein said health-check device comprises:
  • the first measurement system may include measurement means for measuring a forward speed of the aircraft, or indeed measurement means for measuring the altitude of said aircraft.
  • the second system may include measurement means for measuring at least one of the following parameters: the speed of rotation Ng of a gas generator of said engine; a temperature TET of the gas at the inlet of a high-pressure turbine of the engine; a temperature T 45 of the gas at the inlet of a free turbine of said engine; a torque Tq delivered by the engine; and an inlet temperature T 1 of the air at the inlet of the engine.
  • the computer of the processor device may comprise one calculation unit per engine, e.g. a calculation unit of a Full Authority Digital Engine Control (FADEC) engine computer of each engine.
  • FADEC Full Authority Digital Engine Control
  • the storage means may comprise one storage unit per engine, e.g. a storage unit of a FADEC engine computer of each engine.
  • processor device may further comprise an avionics computer communicating with each calculation unit.
  • said processor device is connected to each extraction means for deactivating the air extraction from the engine for checking before triggering the acquisition step and for increasing the amount of air extracted from at least one other engine so as to compensate for such deactivation.
  • the health-check device may further comprise means for deactivating the automatic health check and means for signaling that a health check has been performed.
  • the invention also provides an aircraft provided with such a health-check device.
  • FIG. 1 shows an aircraft provided with a single turbine engine
  • FIGS. 2 and 3 are diagrams explaining the method as applied to a single-engine aircraft
  • FIG. 4 shows an aircraft provided with at last two turbine engines
  • FIG. 5 is a diagram explaining the method as applied to an aircraft provided with at least two turbine engines.
  • FIG. 1 shows an aircraft 1 provided with a rotary wing 300 .
  • the invention may also apply to some other type of aircraft.
  • the aircraft 1 has at least one turbine engine 3 for driving the rotary wing 300 via a main power transmission gearbox (MGB) 2 .
  • Each engine has a gas generator 4 and a turbine assembly 5 .
  • the gas generator comprises a compressor 8 co-operating with a high-pressure turbine 7 of the assembly 5 .
  • the turbine assembly 5 includes a free turbine 6 that is connected to the MGB via a powertrain 9 .
  • this powertrain 9 may be provided with an outlet shaft that is set into rotation by the free turbine.
  • the aircraft 1 of FIG. 1 has one turboshaft engine 3 .
  • the invention proposes to perform automatically the check of the health of at least one turbine engine by means of a health-check device 10 of the aircraft.
  • the health-check device includes a processor device 11 provided with a computer 12 and with storage means 13 on a single-engine aircraft.
  • the processor device may be the FADEC engine computer of the engine.
  • This processor device is connected to a first measurement system 15 for measuring information relating to forward movement of the aircraft through three-dimensional space.
  • the first measurement system includes measurement means 20 for measuring a forward speed VIT of the aircraft and data relating to the altitude of the aircraft 1 .
  • data relating to the altitude is either the pressure altitude ZP of the aircraft, or the outside pressure P 0 of the air outside the aircraft.
  • the processor device 11 If the forward speed VIT is greater than a minimum speed defined by the manufacturer and if, over a given length of time, variation in the data ZP, P 0 relating to altitude is less than a constant defined by the manufacturer, then the processor device 11 considers that the aircraft is flying in level forward flight.
  • the minimum speed is about 50 knots (kts), and the constant limiting the variation in altitude is about 10 meters.
  • a stability verification step STP 2 the stability of the engine for checking is verified by verifying the stability of at least one monitoring parameter Ng, TET, T 45 , Tq, T 1 .
  • the processor device 11 is connected to a second measuring system 15 .
  • the second system 15 transmits at least one signal to the processor device 11 relating to the value of at least one monitoring parameter Ng, TET, T 45 , Tq, T 1 .
  • the processor device 11 acquires a measurement signal giving a measurement of at least one monitoring parameter Ng, TET, T 45 , Tq, T 1 of the engine 3 in compliance with sampling defined by the manufacturer, e.g. of the order of every one-tenth of a second.
  • the processor device 11 performs first filtering of each received signal SIG by a high-pass filter, and it does so over a long first duration TPS 1 , e.g. of the order of 4 minutes.
  • the processor device 11 verifies that a first amplitude A 1 of the signal SIG filtered in this way does not exceed a first threshold defined by the manufacturer.
  • the processor device 11 takes a moving average MOY, over a defined period of the order of 20 seconds, for averaging the value of each monitoring parameter Ng, TET, T 45 , Tq, T 1 , and then, at each instant, the appropriate moving average is subtracted from the value of the signal SIG being studied.
  • the processor device 11 evaluates the moving average MOY 1 of the monitoring parameter being studied, on the basis of a sample SIGPER of the signal SIG corresponding to said period.
  • the processor device 11 compares the first threshold with the difference between the value of the monitoring parameter at the instant Tex and said moving average MOY 1 .
  • the first threshold may be: 2% for the speed of rotation Ng of the gas generator 4 of said engine; 15° C. for the temperature TET of the gas at the inlet of a high-pressure turbine 7 of the engine and for the temperature T 45 of the gas at the inlet of a free turbine 6 of said engine; 2% for torque Tq delivered by the engine; and 2° C. for the inlet temperature T 1 of the air at the inlet of the engine.
  • the processor device 11 performs second filtering of each signal by a high-pass filter, and it does so over a short second duration TPS 2 , e.g. of the order of thirty seconds, in parallel with said first filtering.
  • first duration TPS 1 and the second duration TPS 2 end at the same time.
  • each monitoring parameter is found to be stable for a duration equal to the first duration TPS 1 minus the second duration TPS 2 by applying the appropriate first threshold, then the processor device performs a second stability test in parallel with continuing to perform the first test.
  • the processor device 11 verifies that a second amplitude A 2 of the signal filtered in this way does not exceed a second threshold defined by the manufacturer, the second duration TPS 2 being less than the first duration TPS 1 , and the second amplitude A 2 being less than the first amplitude A 1 .
  • the second threshold may be: 0.5% for the speed of rotation Ng of the gas generator of said engine; 5° C. for the temperature TET of the gas at the inlet of a high-pressure turbine of the engine and for the temperature T 45 of the gas at the inlet of a free turbine of said engine; 0.5% for torque Tq delivered by the engine; and 0.5° C. for the inlet temperature T 1 of the air at the inlet of the engine.
  • the monitoring parameter is then considered to be stable.
  • the processor device 11 automatically triggers an acquisition step STP 3 if each monitoring parameter in question is stable.
  • the processor device 11 may generate a warning by using signaling means 50 to inform the pilot that a health check is beginning.
  • the processor device 11 automatically triggers an evaluation step STP 4 .
  • the aircraft may have a plurality of turbine engines 3 , each engine co-operating with a FADEC engine computer.
  • the computer 12 of the processor device may comprise a calculation unit 12 ′ of each FADEC engine computer.
  • the storage means may contain a storage unit of each FADEC engine computer, each storage unit containing the same instructions.
  • the processor device 11 may include an avionics computer 40 .
  • the avionics computer 40 is connected to signaling means 50 or indeed to deactivation means 60 serving to deactivate the automatic health check.
  • the first measurement system 20 may be connected to each calculation unit 12 ′ of the computer 12 .
  • the second measurement system 15 may include one measurement unit 15 ′ per engine that co-operates with the appropriate calculation unit 12 ′.
  • the avionics computer 40 may designate an engine for checking.
  • the choice of the engine for checking may be established as a function of a strategy defined by the manufacturer and stored in a memory.
  • the FADEC engine computer of said engine 3 for checking then performs the preliminary step STP 1 , and, where applicable, the stability verification step STP 2 .
  • the preliminary step may also be performed by the avionics computer 40 , said avionics computer 40 then communicating with the first measurement system 20 for this purpose.
  • the processor device 11 may request deactivation of air extraction from the engine 3 for checking before triggering the acquisition step STP 3 , and may request an increase of air extraction from at least one other engine 3 to compensate for such deactivation.
  • the health-check device includes adjustment means for adjusting the means MP for extracting air P 3 , it being possible for these adjustment means to be constituted by the FADEC engine computer of each engine.
  • the avionics computer 40 can instruct the FADEC engine computer of the engine for checking to shut off the extraction means MP of said engine for checking.
  • the avionics computer 40 may instruct the FADEC engine computer of at least one other engine to increase the amount of air extracted, by way of compensation.
  • This new stability verification step STP 2 may be identical to the preceding stability verification step, or else it may be implemented by using first and second durations TPS 1 and TPS 2 that are different.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Testing Of Engines (AREA)
US13/737,260 2012-02-06 2013-01-09 Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine Active 2035-01-30 US9222412B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1200341A FR2986506B1 (fr) 2012-02-06 2012-02-06 Procede et dispositif pour realiser un controle de sante d'un turbomoteur d'un aeronef pourvu d'au moins un turbomoteur
FR1200341 2012-02-06

Publications (2)

Publication Number Publication Date
US20130199204A1 US20130199204A1 (en) 2013-08-08
US9222412B2 true US9222412B2 (en) 2015-12-29

Family

ID=47323829

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/737,260 Active 2035-01-30 US9222412B2 (en) 2012-02-06 2013-01-09 Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine

Country Status (5)

Country Link
US (1) US9222412B2 (ko)
EP (1) EP2623748B1 (ko)
KR (1) KR101435138B1 (ko)
CA (1) CA2799933C (ko)
FR (1) FR2986506B1 (ko)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11427353B2 (en) 2019-12-13 2022-08-30 Pratt & Whitney Canada Corp. System and method for testing engine performance in-flight

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3015428B1 (fr) 2013-12-20 2017-04-28 Eurocopter France Installation motrice disposant d'un moteur secondaire compensant les pertes de puissance des moteurs principaux pour un aeronef a voilure tournante
FR3027061B1 (fr) * 2014-10-10 2019-10-25 Safran Helicopter Engines Procede et dispositif de notification d'une autorisation d'arret complet d'un moteur a turbine a gaz d'aeronef
US10809156B2 (en) 2016-02-15 2020-10-20 General Electric Company Automated system and method for generating engine test cell analytics and diagnostics
FR3052747B1 (fr) 2016-06-17 2018-05-25 Airbus Operations (S.A.S.) Procede de surveillance des moteurs d'un aeronef
US10962448B2 (en) * 2016-06-17 2021-03-30 Airbus Operations Sas Method for monitoring the engines of an aircraft
FR3064680B1 (fr) * 2017-04-03 2019-04-05 Safran Helicopter Engines Procede de verification de la puissance maximale disponible d'une turbomachine d'un aeronef equipe de deux turbomachines
US10692388B1 (en) * 2018-12-14 2020-06-23 General Electric Company Global environmental data and application methods for understanding engine health and maintenance
US11474494B2 (en) * 2019-03-22 2022-10-18 Hamilton Sundstrand Corporation Method for simulating an N1 and N2 speed vibration composite input for development and/or model based testing of engine control hardware and embedded software
US11391218B2 (en) * 2019-03-22 2022-07-19 Pratt & Whitney Canada Corp. Method and system for setting power of an aircraft engine
US11560850B2 (en) 2019-03-29 2023-01-24 Pratt & Whitney Canada Corp. Detection of abnormal engine starts
FR3095196B1 (fr) * 2019-04-17 2021-12-03 Airbus Helicopters Procédé et dispositif pour estimer la santé d’une installation motrice d’un aéronef pourvu d’au moins un moteur et d’un filtre colmatable filtrant de l’air en amont du moteur
US11667392B2 (en) * 2019-06-20 2023-06-06 Pratt & Whitney Canada Corp. Method and system for operating a rotorcraft engine
US20210025338A1 (en) * 2019-07-26 2021-01-28 Pratt & Whitney Canada Corp. System and method for operating a turboprop engine
GB201915308D0 (en) * 2019-10-23 2019-12-04 Rolls Royce Plc Turboshaft
US11326468B2 (en) * 2019-11-08 2022-05-10 Pratt & Whitney Canada Corp. Methods and systems for operating a gas turbine engine
CN112173169A (zh) * 2020-09-25 2021-01-05 中国直升机设计研究所 一种三发直升机发动机功率自动检查方法
FR3123324B1 (fr) 2021-05-31 2023-04-21 Airbus Helicopters Procédé d’aide au pilotage d’un giravion en hautes altitudes grâce à l’apport d’une puissance mécanique provenant d’une installation motrice électrique
FR3136748A1 (fr) 2022-06-15 2023-12-22 Airbus Helicopters Procédé de diagnostic automatique pour au moins un moteur équipant un aéronef, aéronef et ensemble mettant en œuvre le procédé

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2899640A1 (fr) 2006-04-05 2007-10-12 Eurocopter France Procede et dispositif pour realiser un controle de l'etat de sante d'un turbomoteur d'un giravion bimoteur
FR2902408A1 (fr) 2006-06-19 2007-12-21 Eurocopter France Equilibrage en puissance de deux turbomoteurs d'un aeronef
EP1970786A2 (en) 2007-03-15 2008-09-17 Honeywell International Inc. Automated engine data diagnostic analysis
US7487029B2 (en) 2004-05-21 2009-02-03 Pratt & Whitney Canada Method of monitoring gas turbine engine operation
US8068997B2 (en) 2009-02-06 2011-11-29 Honeywell International Inc. Continuous performance analysis system and method
US20130204468A1 (en) * 2012-02-06 2013-08-08 Eurocopter Method and a device for performing a health check of a turbine engine of an aircraft having at least one such engine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8321118B2 (en) 2008-12-23 2012-11-27 Honeywell International Inc. Operations support systems and methods with power assurance

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7487029B2 (en) 2004-05-21 2009-02-03 Pratt & Whitney Canada Method of monitoring gas turbine engine operation
FR2899640A1 (fr) 2006-04-05 2007-10-12 Eurocopter France Procede et dispositif pour realiser un controle de l'etat de sante d'un turbomoteur d'un giravion bimoteur
US7769521B2 (en) 2006-04-05 2010-08-03 Eurocopter Method and a device for performing a check on the state of health of a turbine engine of a twin-engined rotorcraft
FR2902408A1 (fr) 2006-06-19 2007-12-21 Eurocopter France Equilibrage en puissance de deux turbomoteurs d'un aeronef
US20080275597A1 (en) 2006-06-19 2008-11-06 Eurocopter Balancing the power of two turboshaft engines of an aircraft
EP1970786A2 (en) 2007-03-15 2008-09-17 Honeywell International Inc. Automated engine data diagnostic analysis
US20080228338A1 (en) 2007-03-15 2008-09-18 Honeywell International, Inc. Automated engine data diagnostic analysis
US8068997B2 (en) 2009-02-06 2011-11-29 Honeywell International Inc. Continuous performance analysis system and method
US20130204468A1 (en) * 2012-02-06 2013-08-08 Eurocopter Method and a device for performing a health check of a turbine engine of an aircraft having at least one such engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Search Report and Written Opinion; Application No. FR 1200341; dated Sep. 27, 2012.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11427353B2 (en) 2019-12-13 2022-08-30 Pratt & Whitney Canada Corp. System and method for testing engine performance in-flight

Also Published As

Publication number Publication date
FR2986506B1 (fr) 2015-06-26
KR101435138B1 (ko) 2014-09-01
CA2799933C (fr) 2014-05-20
EP2623748A1 (fr) 2013-08-07
US20130199204A1 (en) 2013-08-08
EP2623748B1 (fr) 2015-02-25
CA2799933A1 (fr) 2013-08-06
FR2986506A1 (fr) 2013-08-09
KR20130090850A (ko) 2013-08-14

Similar Documents

Publication Publication Date Title
US9222412B2 (en) Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine
US8666568B2 (en) Method and a device for performing a health check of a turbine engine of an aircraft having at least one such engine
US9815568B2 (en) Device for monitoring a power transmission system of an aircraft, an aircraft provided with the device, and the method used
KR102339468B1 (ko) 쌍발 엔진 헬리콥터의 제 1 터빈 엔진의 고장을 탐지하는 것 및 제 2 터빈 엔진을 작동시키는 것을 위한 방법, 및 대응하는 장치
US9346553B2 (en) Balancing the power of two turboshaft engines of an aircraft
US8121773B2 (en) Method and an instrument for determining the limiting parameter of a turboshaft engine
US7769521B2 (en) Method and a device for performing a check on the state of health of a turbine engine of a twin-engined rotorcraft
CN105314117B (zh) 用于检测涡轮轴引擎的进气口处的结冰的方法和设备
KR101451950B1 (ko) 항공기 성능의 최적화 방법, 장치, 및 항공기
EP3173890B1 (en) Fault detection methods and systems
US9821916B2 (en) Method and a device for managing a loss of power on a three-engined power plant
US10017268B2 (en) Method of monitoring at least one freewheel of a rotary wing aircraft, and an aircraft
RU2631557C1 (ru) Способ определения в полете изгибных напряжений на валу несущего винта вертолета с торсионной втулкой несущего винта
EP3106649A1 (en) Aircraft gas turbine propulsion engine control without aircraft total air temperature sensors
US11499483B2 (en) Method and a device for estimating the health of a power plant of an aircraft having at least one engine and a cloggable filter filtering air upstream from the engine
US9157375B2 (en) Method and a device for optimizing the utilization of an engine
Idzikowski et al. FLiGht tests oF tUrBoprop enGine With reVerse air intaKe sYsteM

Legal Events

Date Code Title Description
AS Assignment

Owner name: EUROCOPTER, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CAMHI, EMMANUEL;BORCHERS, GUIDO;REEL/FRAME:029948/0426

Effective date: 20130121

AS Assignment

Owner name: AIRBUS HELICOPTERS, FRANCE

Free format text: CHANGE OF NAME;ASSIGNOR:EUROCOPTER;REEL/FRAME:032813/0001

Effective date: 20140107

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCF Information on status: patent grant

Free format text: PATENTED CASE

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 4

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 8